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1
Zhu, Yan. "Longitudinal control laws design for a flying wing aircraft." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7423.
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This research is concerned with the flight dynamic, pitch flight control and flying
qualities assessment for the reference BWB aircraft. It aims to develop the
longitudinal control laws which could satisfy the flying and handing qualities
over the whole flight envelope with added consideration of centre of gravity (CG)
variation.
In order to achieve this goal, both the longitudinal stability augmentation system
(SAS) and autopilot control laws are studied in this thesis. Using the pole
placement method, two sets of local Linear-Time-Invariant (LTI) SAS controllers
are designed from the viewpoints of flying and handing qualities assessment
and wind disturbance checking. The global gain schedule is developed with the
scheduling variable of dynamic pressure to transfer gains smoothly between
these two trim points. In addition, the poles movement of short period mode with
the varying CG position are analysed, and some approaches of control system
design to address the problem of reduced stability induced by CG variation are
discussed as well. To achieve the command control for the aircraft, outer loop
autopilot both pitch attitude hold and altitude hold are implemented by using the
root locus method.
By the existing criteria in MIL-F-8785C specifications being employed to assess
the augmented aircraft response, the SAS linear controller with automatic
changing gains effectively improve the stability characteristic for the reference
BWB aircraft over the whole envelope. Hence, the augmented aircraft equals to
a good characteristic controlled object for the outer loop or command path
design, which guarantee the satisfactory performance of command control for
the BWB aircraft.
The flight control law for the longitudinal was completed with the SAS controller
and autopilot design. In particular, the SAS was achieved with Level 1 flying and
handing qualities, meanwhile the autopilot system was applied to obtain a
satisfactory pitch attitude and altitude tracking performance.
2
Pergamalis, Nikolaos. "Conceptual design, flying and handling qualities of a supersonic transport aircraft." Thesis, KTH, Flygdynamik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-211167.
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The purpose of this project is the design of a supersonic aircraft that is able to meet the market’s requirements, be economically viable and mitigate the current barriers. The initial requirements of the design have been set according to the understanding obtained from a brief market research, taking into account the market needs, in addition to the economical and environmental restrictions. The conceptual design proposed is a supersonic transport able to execute transatlantic flights carrying 15 passengers. The aerodynamics, propulsion data and weight of the design have been estimated using empirical relations and experimental data found in references. The design has been evaluated regarding its performance, stability, flying and handling qualities. The relevant models have been created using the software Matlab, while the flight testing has been executed at the Merlin MP521 engineering flight simulator. Finally, a discussion is made about the environmental impact of the supersonic transport, focusing on the aerodynamic noise, generated by the sonic boom, and the air pollutants emissions.
3
Lee, Brian P. "Pilot and control system modelling for handling qualities analysis of large transport aircraft." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/10203.
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The notion of airplane stability and control being a balancing act between
stability and control has been around as long as aeronautics. The Wright
brothers’ first successful flights were born of the debate, and were successful at
least in part because they spent considerable time teaching themselves how to
control their otherwise unstable airplane.
This thesis covers four aspects of handling for large transport aircraft: large
size and the accompanying low frequency dynamics, the way in which lifting
surfaces and control system elements are modelled in flight dynamics analyses,
the cockpit feel characteristics and details of how pilots interact with them, and
the dynamic instability associated with Pilot Induced Oscillations.
The dynamics associated with large transport aircraft are reviewed from the
perspective of pilot-in-the-loop handling qualities, including the effects of
relaxing static stability in pursuit of performance. Areas in which current design
requirements are incomplete are highlighted. Issues with modelling of dynamic
elements which are between the pilot’s fingers and the airplane response are
illuminated and recommendations are made.
Cockpit feel characteristics are examined in detail, in particular, the nonlinear
elements of friction and breakout forces. Three piloted simulation experiments
are described and the results reviewed. Each was very different in nature, and
all were designed to evaluate linear and nonlinear elements of the cockpit feel
characteristics from the pilot’s point of view. These included understanding the
pilot’s ability to precisely control the manipulator itself, the pilot’s ability to
command the flight path, and neuro-muscular modelling to gain a deeper
understanding of the range of characteristics pilots can adapt to and why.
Based on the data collected and analyzed, conclusions are drawn and
recommendations are made. Finally, a novel and unique PIO prediction criterion is developed, which is based
on control-theoretic constructs. This criterion identifies unique signatures in the
dynamic response of the airplane to predict the onset of instability.
4
de, Castro Helena V. "Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft." Thesis, Cranfield University, 2003. http://hdl.handle.net/1826/119.
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The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic BWB large transport aircraft concept.
Longitudinal and lateral-directional static and dynamic stability analysis using aerodynamic data representative of different BWB configurations enabled a better understanding of the BWB aircraft characteristics and identification of the mechanisms that influence its behaviour. The static stability studies revealed that there is limited control power both for the longitudinal and lateral-directional motion. The solution for the longitudinal problem is to limit the static margins to small values around the neutral point, and even to use negative static margins. However, for the directional control problem the solution is to investigate alternative ways of generating directional control power. Additional investigation uncovered dynamic instability due to the low and negative longitudinal and directional static stability. Furthermore, adverse roll and yaw responses were found to aileron inputs.
The implementation of a pitch rate command/attitude hold flight control system (FCS) improved the longitudinal basic BWB characteristics to satisfactory levels, or Level 1, flying and handling qualities (FHQ). Although the lateral-directional command and stability FCS also improved the BWB flying and handling qualities it was demonstrated that Level 1 was not achieved for all flight conditions due to limited directional control power.
The possibility to use the conventional FHQs criteria and requirements for FCS design and FHQs assessment on BWB configurations was also investigated. Hence, a limited set of simulation trials were undertaken using an augmented BWB configuration. The longitudinal Bandwidth/Phase delay/Gibson dropback criteria, as suggested by the military standards, together with the Generic Control Anticipation Parameter (GCAP) proved possible to use to assess flying and handling qualities of BWB aircraft. For the lateral-directional motion the MIL-F-8785C criteria were used. Although it is possible to assess the FHQ of BWB configuartions using these criteria, more research is recommended specifically on the lateral-directional FHQs criteria and requirements of highly augmented large transport aircraft.
5
Foster, Tyler Michael. "Dynamic Stability and Handling Qualities of Small Unmanned-Aerial-Vehicles UNMANNED-AERIAL-VEHICLES." BYU ScholarsArchive, 2004. https://scholarsarchive.byu.edu/etd/219.
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General aircraft dynamic stability theory was used to predict the natural frequencies, damping ratios and time constants of the dynamic modes for three specific small UAVs with wingspans on the scale from 0.6 meters to 1.2 meters. Using USAF DatCom methods, a spreadsheet program for predicting the dynamic stability and handling qualities of small UAVs was created for use in the design stage of new small UAV concept development. This program was verified by inputting data for a Cessna-182, and by then comparing the program output with that of a similar program developed by DAR Corporation. Predictions with acceptable errors were made for all of the dynamic modes except for the spiral mode. The design tool was also used to verify and develop dynamic stability and handling qualities design guidelines for small UAV designers. Using this design tool, it was observed that small UAVs tend to exhibit higher natural frequencies of oscillation for all of the dynamic modes. Comparing the program outputs with military handling qualities specifications, the small UAVs at standard configurations fell outside the range of acceptable handling qualities for short-period mode natural frequency, even though multiple test pilots rated the flying qualities as acceptable. Using dynamic scaling methods to adjust the current military standards for the short period mode, a new scale was proposed specifically for small UAVs. This scale was verified by conducting flight tests of three small UAVs at various configurations until poor handling qualities were observed. These transitions were observed to occur at approximately the boundary predicted by the new, adjusted scale.
6
Lesiário, Ana. "Parametric Studies on UAV Flying Qualities." Thesis, KTH, Reglerteknik, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-105898.
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When developing an aircraft, one of several important aspects is to predict and properly design the dynamic behaviour of the aircraft. This holds for manned aircraft as well as for UAVs. The optimal dynamic behaviour for an aircraft depends on the mission or purpose: for a certain use an aircraft should be agile, other may require a more stable one. In aeronautics, the properties that describe the aircraft ecacy with respect to some task are known as ying qualities, and our goal is to study their dependence on some design parameters. As a test model we use an existing UAV. After deriving its 6-DOF dynamic model and assessing its baseline characteristics, we perform parametric studies. The strategy followed is divided in two steps: the rst consists on analyzing ying qualities sensitivity to changes in model parameters. The second step studies how specific design changes affect model parameters. Because the rst step only depends on the dynamic model form, we verify, by testing two other dierent aircrafts, that conclusions drawn from this step are valid to other congurations. Finally we show how results from parametric studies can be used to improve the UAV ying qualities regarding a certain mission, through the introduction of slight modications on baseline design.
7
Lawrence, Ben. "The flying qualities of the Wright flyers." Thesis, University of Liverpool, 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.408567.
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Ahmad, Shah Shahrul. "Improved autogyro flying qualities using automatic control methods." Thesis, University of Glasgow, 2018. http://theses.gla.ac.uk/39052/.
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An autogyro or Autogiro is a unique type of rotary-wing aircraft that was successfully flown in the 1920s, many years before the first helicopter came to service. As far as the rotorcraft technology is concerned, the technical issues addressed by autogyros were eventually rectified and paved the way for the success of helicopter development. When helicopter became more popular and accepted in the civil aviation industry in the 1940s, autogyros were nearly forgotten and the popularity slowly diminished. The re-emergence of autogyros in the last two decades in hobby and sports flight activities, however, coincides with bad safety records due to stability issues. At the time of this writing, there are no specific flying qualities standards to be em- ployed as guidelines to design a light autogyro with good stability attributes. The only requirements available are addressed in the BCAR Section T airworthiness standard for light autogyros which only prescribes some basic dynamic stability requirements for the vehicle. For existing conventional light autogyros which mostly of 'home-built' type, complying with the airworthiness standards would be an issue as most of them were built beforehand. From these concerns, this Thesis aims to improve the flying qualities performance of existing light autogyros through automatic flight control methods, as one of the ways to practically achieve the required performance. Consequently, specific flying qualities requirements for light autogyros must first be proposed as preliminary guidelines for design and flying qualities improvement. A generic mathematical model of light autogyros named ARDiS is developed based on the 'multiblade' simulation ap- proach which is computationally cost-effective. This model was successfully validated against real autogyro flight data and later implemented in the control enhancement of the vehicle. The control enhancement was developed using classical approaches with limitation in size and simplicity of the vehicle as a light aircraft. Proper actuation control hard- ware was separately modelled and deployed into the autogyro to demonstrate a higher dynamics in the control mechanism so that a more realistic attitude behaviour of the vehicle is presented. This control enhancement was successfully evaluated with both, linear and nonlinear simulations according to the proposed autogyro flying qualities attributes. All presented results signify a higher possibility of improving the flying qualities of currently used and future built light autogyros through control enhance- ment.
9
Field, Edmund. "Flying qualities of transport aircraft : precognitive or compensatory?" Thesis, Cranfield University, 1995. http://dspace.lib.cranfield.ac.uk/handle/1826/10636.
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The introduction of fly-by-wire electronic flight control systems into transport aircraft
has given the flying qualities engineer the opportunity to optimise the flying qualities of
these aircraft for their specific tasks.
With this technology has come the opportunity to introduce new technologies into the
cockpit, such as non-linked or backfed sidesticks and non-backfed throttle levers. A
comparative survey of airline pilots flying such a very high technology unconventional
aircraft and a high technology but conventional aircraft suggests that these technologies
may reduce the available channels of communication to the pilot in the very high
technology aircraft, resulting in the possibility of reduced situational awareness.
A closed loop piloted simulation survey of ten transport aircraft in current operation was
undertaken which demonstrated that they all suffered from flying qualities deficiencies,
limiting the performance that the pilot could achieve. In particular poor dynamics
precluded the pilot adopting tight closed loop, or compensatory, control. Instead it was
necessary to adopt a more open loop, precognitive, technique with medium frequency
modulation, resulting in a degradation in landing performance.
Through appropriate flight control system design it should be possible to produce aircraft
that can be flown using the full range of control inputs from open to closed loop. The
major study of this thesis assessed, through piloted simulation evaluations, the suitability
of a wide range of longitudinal commanded response types for the approach and landing
tasks. It was concluded that a response type that closely resembles that of angle of attack
is optimum for these tasks due to its conventional characteristics of speed stability on the
approach and monotonic stick forces in the flare. Such a system, appropriately
implemented, should allow the transport aircraft pilot the full range of piloted control
inputs, from open loop, precognitive, to closed loop, compensatory, resulting in
improved landing performance.
10
Field, Edmund J. "Flying qualities of transport aircraft : precognitive or compensatory?" Thesis, Cranfield University, 1995. http://dspace.lib.cranfield.ac.uk/handle/1826/10636.
Full textAbstract:
The introduction of fly-by-wire electronic flight control systems into transport aircraft has given the flying qualities engineer the opportunity to optimise the flying qualities of these aircraft for their specific tasks. With this technology has come the opportunity to introduce new technologies into the cockpit, such as non-linked or backfed sidesticks and non-backfed throttle levers. A comparative survey of airline pilots flying such a very high technology unconventional aircraft and a high technology but conventional aircraft suggests that these technologies may reduce the available channels of communication to the pilot in the very high technology aircraft, resulting in the possibility of reduced situational awareness. A closed loop piloted simulation survey of ten transport aircraft in current operation was undertaken which demonstrated that they all suffered from flying qualities deficiencies, limiting the performance that the pilot could achieve. In particular poor dynamics precluded the pilot adopting tight closed loop, or compensatory, control. Instead it was necessary to adopt a more open loop, precognitive, technique with medium frequency modulation, resulting in a degradation in landing performance. Through appropriate flight control system design it should be possible to produce aircraft that can be flown using the full range of control inputs from open to closed loop. The major study of this thesis assessed, through piloted simulation evaluations, the suitability of a wide range of longitudinal commanded response types for the approach and landing tasks. It was concluded that a response type that closely resembles that of angle of attack is optimum for these tasks due to its conventional characteristics of speed stability on the approach and monotonic stick forces in the flare. Such a system, appropriately implemented, should allow the transport aircraft pilot the full range of piloted control inputs, from open loop, precognitive, to closed loop, compensatory, resulting in improved landing performance.
11
Lindqvist, Daniel. "Methodology For Evaluating Flying Qualities From Desktop Simulator." Thesis, Luleå tekniska universitet, Rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-77354.
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A modern ghter aircraft has an advanced ight control system which highly augmentsthe control inputs from the pilot. To verify a new iteration of the control system is a timeconsuming and expensive task. It is desired to nd qualities that is not satisfactory to thepilot as early as possible in the verication process to reduce the cost for design changes.The primary objective of this thesis is to develop methods that can be used for automaticalevaluation of aircraft ying qualities from the data provided by a desktop simulator. A desktopsimulator is cheap to use compared to ight tests and tests with a pilot in a simulator.Only ghter aircraft in the precision ight phase are studied however the methods developedcould easily be extended to include other types of aircraft and other phases of ight.To evaluate the ying qualities two sets of criteria are used the MIL-F-8785C standardand the Gibson criteria. The MIL-F-8785C standard uses a second order linear system toevaluate the aircraft's ying qualities. The linear system is estimated from the nonlineardata and evaluated against the MIL-F-8785C standard. The Gibson criteria studies the timeand frequency domain directly and are designed to work with highly augmented aircraft.The set of Gibson criteria used in this thesis primary evaluates data from the time domainhowever one criterion from the frequency domain is studied.The methods developed to evaluate the ying qualities from the MIL-F-8785C standardonly works for a small part of the ight envelope furthermore they show a large dierencefor what is considered acceptable ying qualities. Because of this the methods developed forthe MIL-F-8785C standard are considered not to be suited for evaluating ying qualities forhighly augmented aircraft. The methods developed to evaluate the ying qualities againstthe Gibson criteria works for a large part of the ight and also show a high accuracy. Thismakes the methods suited for evaluation of the ying qualities.
12
Isaksson, Ola. "Classification of Flying Qualities with Machine Learning Methods." Thesis, KTH, Flygdynamik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-302145.
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The primary objective of this thesis is to evaluate the prospect of machine learning methods being used to classify flying qualities based on simulator data (with the focus being on pitch maneuvers). If critical flying qualities could be identified earlier in the verification process, they can be further invested in and focused on with less cost for design changes of the flight control system. Information from manned simulations with given flying quality levels are used to create a replication of the performed pitch maneuver in a desktop simulator. The generated flight data is represented by different measures in the classification to separately train and test the machine learning models against the given flying quality level. The models used are Logistic Regression, Support Vector Machines with radial basis functions (RBF), linear and polynomial kernels along with Artificial Neural Networks. The results show that the classifiers correctly identify at least 80% of cases with critical flying qualities. The classification shows that the statistical measures of the time signals and first order time derivatives of pitch, roll and yaw rates are enough for classification within the scope of this thesis. The different machine learning models show no significant difference in performance in the scope of this thesis. In conclusion, machine learning methods show good potential for classification of flying qualities, and could become an important tool for evaluating flying qualities of large amounts of simulations, in addition to manned simulations.Huvuduppgiften med detta examensarbete är att utvärdera huruvida maskininlärning kan användas för att klassificera flygkvaliteter från simulatordata (där fokus ligger på att utvärdera tippmanövrar). Om kritiska flygkvaliteter kan identifieras tidigare i verifikationsprocessen, kan resurser fokuseras för att åtgärda problemet tidigt med mindre kostnader för ändringar av styrsystemet. Information från bemannade simuleringar där flygkvalitetsnivåer har angetts av pilot används för att återskapa tippmanövern i skrivbordssimulatorn. Den genererade flygdatan representeras av olika mått i klassificeringen för att separat träna och testa maskininlärningsmodellerna mot den givna flygkvalitetsnivån. De modeller som används i rapporten är logistisk regression, stödvektormaskiner med radiella basfunktioner (RBF), linjär och polynomisk kärna samt artificiella neurala nätverk. Resultaten visar att klassificerarna korrekt identifierar över 80% av fallen med kritiska flygkvaliteter. Klassificeringen visar att statistiska mått av tidssignalen och första ordningens tidsderivator i tipp, roll och gir är tillräckligt för klassificering inom gränserna av detta examensarbete. De olika maskininlärningsmodellerna visar inga signifikanta skillnader i prestanda med datan som används. Sammanfattningsvis kan maskininlärningsmodellerna anses ha god potential för klassificering av flygkvaliteter, och kan vara ett viktigt verktyg för att klassificera flygkvaliteter för stora mängder flygdata, som komplement till bemannade simuleringar.
13
Chiu, Alton Pak-Hin. "Flying Qualities Built-In-Test For Unmanned Aerial Systems." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/712.
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This paper presents a flying qualities built-in-test for UAS application with the scope limited to the longitudinal axis. A doublet input waveform excites the AV and both α and q are used by EUDKF to estimate the A and B matrices which are short period approximations of the system. ζ, ω, GM, PM, observability, and controllability are calculated to determine flying qualities with the results displayed to the AVO in a color-coded, easy to interpret display.
While SID algorithms have been flying in vehicles with adaptive control schemes, vehicles with other schemes (such as classical feedback) lack this built-in self assessment tool. In addition, adaptive control SID results are not analyzed and displayed but instead used internally. This work intends to extend this self-assessment option to all UASs regardless of control scheme as a “plug-and-play” add-on by building a reliable and robust tool that requires little tuning.
14
Choi, June. "Application of hypersonic vehicle flying qualities criteria and computational considerations." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/47356.
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Tomac, Maximilian. "Adaptive-fidelity CFD for predicting flying qualities in preliminary aircraft design." Licentiate thesis, KTH, Aerodynamik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-31400.
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To reduce development cost and to avoid late design fixes in aircraft design, methods that are fast and economic in estimating the aerodynamic characteristics of complex flight vehicles at the preliminary design stage are desired. This work and thesis focus on the adaptive-fidelity CFD approach, with emphasis on the high end of the CFD tools available today. The core idea of the method is to use computationally cheap modeling in the part of the flight envelope where it is applicable. When the complexity in the flow field increases more details and realism is included in the mathematical model, at a computationally higher cost. A typical case where this would be required could be at the border of the flight envelope, where flow phenomena such as shocks, flow separation, and interacting vortex systems could occur. Since the number of cases needed to resolve the flight envelope could be in the order of ten thousands automation is required. The bottlenecks are the discretization of the fluid volume and evaluation of raw CFD data and post processing of the data. These issues are also discussed in this work. The method has been tested on two real flying aircraft, the X-31 delta-winged aircraft with vector thrust, and the Ranger 2000 Jet trainer, as well as on the SACCON preliminary wing-body UCAV design. The results provide improved understanding of the usefulness of this method as an analysis tool during the preliminary design phase all the way into the flight test diagnostic phase of a new aircraft.QC 20110314
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Bernabè, Matteo. "Multi-rotor aircraft flying qualities assessment by means of inverse simulation." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018. http://amslaurea.unibo.it/15910/.
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This thesis work wants to investigate in how complex the mathematical model of a multi-rotor drone has to be, in order to simulate three different flight conditions: impulsive responses, vertical and horizontal flight.
This is done by exploiting a technique called inverse simulation.
Also the two autopilot used to control the model has been designed to be as close as possible to the real one.
The results obtained with Simulink are then compared with the telemetry data collected during the real flight by the Pixhawk flight controller.
17
McFarlane, Cormac. "An investigation of flying qualities for fixed wing unmanned aerial vehicles." Thesis, University of Bristol, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.508060.
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Cotting, Malcolm Christopher. "Evolution of Flying Qualities Analysis: Problems for a New Generation of Aircraft." Diss., Virginia Tech, 2010. http://hdl.handle.net/10919/26781.
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A number of challenges in the development and application of flying qualities criteria for modern aircraft are addressed in this dissertation. The history of flying qualities is traced from its origins to modern day techniques as applied to piloted aircraft. Included in this historical review is the case that was made for the development of flying qualities criteria in the 1940's and 1950's when piloted aircraft became prevalent in the United States military. It is then argued that UAVs today are in the same context historically as piloted aircraft when flying qualities criteria were first developed.
To aid in development of a flying qualities criterion for UAVs, a relevant classification system for UAVs. Two longitudinal flying qualities criteria are developed for application to autonomous UAVs. These criteria center on mission performance of the integrated aircraft and sensor system. The first criterion is based on a sensor platform's ability to reject aircraft disturbances in pitch attitude. The second criterion makes use of energy methods to create a metric to quantify the transmission of turbulence to the sensor platform. These criteria are evaluated with airframe models of different classes of air vehicles using the CASTLE 6 DOF simulation.
Another topic in flying qualities is the evaluation of nonlinear control systems in piloted aircraft. A L1 adaptive controller was implemented and tested in a motion based, piloted flight simulator. This is the first time that the L1 controller has been evaluated for piloted handling qualities. Results showed that the adaptive controller was able to recover good flying qualities from a degraded aircraft.
The final topic addresses a less direct, but extremely important challenge for flying qualities research and education: a capstone course in flight mechanics teaching flight test techniques and featuring a motion based flight simulator was implemented and evaluated. The course used a mixture of problem based learning and role based learning to create an environment where students could explore key flight mechanics concepts. Evaluation of the course's effectiveness to promote the understanding of key flight mechanics concepts is presented.Ph. D.
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Samuelsson, Mikael. "Evaluation of Stability and Flying Qualities of a Light Unmanned Aerial Vehicle (UAV)." Thesis, KTH, Flygdynamik, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-102078.
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The objective of this study was to evaluate the ying qualities of a light unmanned aerial vehicle (UAV) developed by the Thai company AVIA Satcom Co., Ltd. Based on the study changes in design was to be suggested to meet stability requirements and recommendations from European Aviation Safety was based on two dierent analyses. First, the stability characteristics in terms of stability modes were examined by creating a flight dynamics model of the studied airplane. Secondly the controllability of the vehicle was investigated by examining the control surfaces. It was found that the original design of the UAV was dynamically unstable and that the control surfaces were too large making the airplane di-cult to y in trim condition. By studying the stability characteristics of the simulated airplane it could be concluded that the UAV was dynamically stable for the improved design and thereby meet the requirements and recommendations.
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Gautrey, Jim. "Flying qualities and flight control system design for a fly-by-wire transport aircraft." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/9594.
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Fly-by-wire flight control systems are becoming more common in both civil and
military aircraft. These systems give many benefits, but also present a new set of
problems due to their increased complexity compared to conventional systems and
the larger choice of options that they provide. The work presented here considers
the application of fly-by-wire to a generic regional transport aircraft. The flying qualities criteria used for typical flying qualities evaluations are described
briefly followed by analysis of several past transport aircraft flying qualities programmes against these criteria. From these results, some control law independent
design requirements are formulated for a civil aircraft for the approach and landing
task. These control law independent flying qualities criteria are intended to be used
with any generic rate-like control law for a transport aircraft and enabled a number
of different control laws to be designed.
The results of a number of flying qualities evaluations are presented. Both an ILS
approach task and a formation flying task were used. The effects of windshear
were also considered. It was found that control laws which maintain flight path are
suitable for the ILS approach task, while most rate-like response characteristics give
good flying qualities for the formation flying task.
Finally, the conclusions drawn from these evaluations are presented, and both the
Civil and Military current airworthiness requirements are assessed.
In addition to the flying qualities work, a study is made of the management issues
associated with fly-by-wire design. A fly-by-wire aircraft design programme was
proposed and the project management issues associated with this were considered.
A timescale was proposed for the design process for a generic regional aircraft, and
the critical path for this process is presented.EPSRC; Avro International Aerospace.
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Zhang, Mengmeng. "Application and Development of the CEASIOM-SUMO-EDGE Suite for Rapid AeroData Assessment of Aircraft Flying Qualities." Licentiate thesis, KTH, Aerodynamik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-34345.
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In aircraft design, methods for rapid aerodata assessment and data screening at early stages are instrumentalin reducing development cost and first-time-right processes. New efficient tools for the analysis can easethe transition as the traditional and rigidly structured sequential design process gives way to a concurrentmulti-disciplinary process with the compressed time-span required in the competition for market shares. The CEASIOM-SUMO-EDGE software suite provides a way from initial sizing to stability and control design andassessment, including effects of aero-elasticity. CEASIOM ongoing and further development is driven by user needs, and the thesis reports on fourdifferent design and analysis cases which required enhancement of CEASIOM in several respects. The validation study on the B-747 with its multitude of control surfaces required generalizationof control surface definition and modeling. The clean-sheet design of the TransCruiser Mach 0.97passenger transport required compilation, fusion, and screening of aerodynamics data from many sourcesand in different formats. The DanBus and the asymmetrical twin-prop pusher-puller configuration required translationof geometry representation and development of simple propeller models in the automatic meshgeneration and CFD analysis. The way forward is provided by adoption of common data formats and geometry (and structural, etc.)modeling conventions. To this end the current proprietary XML format should be replaced by a more generalXML system such as CPACS under development at DLR which will be made public in the near future.QC 20110629
SimSAC, 6th EU Framework Programme
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Renfrow, Joseph A. "A comparison of the use of classical and modern control design techniques for improving the lateral-directional powered approach flying qualities of the F-14 aircraft." Thesis, This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-07292009-090506/.
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Truong, Quang Huy. "Méthodes d'asservissement visuel pour l'appontage d'hélicoptères." Thesis, Toulouse, ISAE, 2018. http://www.theses.fr/2018ESAE0008/document.
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Cette thèse s’inscrit dans le domaine de l’automatique, et a pour but de fournir des outils utiles à l’atterrissage en mer d’hélicoptères (sur navire ou plateforme) et employés dans le cadre d’un potentiel pilotage automatique. L’objectif a donc été de développer une série de lois de commande pilotées manuellement, puis commandées de façon autonome à l’aide d’informations caméra. Les lois ainsi développées à l’aide de modèles dynamiques d’hélicoptères, limitations mécaniques incluses, se basent sur les critères de Qualité de Vol issus de la norme ADS-33. L’ensemble a fait appel à une approche anti-windup pour améliorer la robustesse face aux situations d’actionneurs en saturation. Enfin les lois issues de ces travaux ont été testées en temps-réel sur le banc de pilotage d’hélicoptères de l’ONERA Salon-de-ProvenceThis thesis is related to the automatic & control engineering field, and itsmain goal is to provide useful tools for ship landing missions, tools that can be used fora potential autopilot. The objective has been to develop a series of control laws manuallypiloted, then automatically controlled by visual servoing using identified image features. Thelaws developped thanks to helicopter models with mechanical limitations were based on flyingqualities criteria from the ADS-33 standard. The process also defines an anti-windup approachto cope with actuator saturations. Finally the main results were assessed in real time withthe ONERA rotorcraft flight test bench at ONERA Salon-de-Provence
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Celere, André Luis. "Método para a avaliação do ganho empregado pelo piloto em ensaios de PIO." Universidade de São Paulo, 2009. http://www.teses.usp.br/teses/disponiveis/18/18149/tde-24072009-113945/.
Full textAbstract:
Um método para avaliação do uso de ganho adequado em ensaios de verificação de PIO (Pilot Induced Oscillations) é apresentado. As tarefas de manobra sintética (Synthetic Tracking Task) são utilizadas para demonstração. A teoria é baseada no conceito de entropia estatística proveniente da teoria da informação e no modelo estrutural do piloto humano. O método é apresentado para manobras executadas no eixo lateral e oferece uma medida do ganho humano utilizado durante a sua execução em malha-fechada. Para a modelagem da planta é utilizado modelo black-box com equacionamento de espaço de estados e identificação de parâmetros. Dados de ensaios em voo provenientes de uma aeronave de transporte certificada FAR-25 são utilizados para medir a razão entre o tempo gasto pelo piloto humano em uma malha fechada em posição versus o tempo em uma malha de derivada da posição (roll vs. roll rate). Esta medida é proposta como validadora da execução correta do ensaio.A method is proposed to verify losed-loop adequate flight test piloting gain in PIO aircraft certification. The synthetic tracking task PIO flight test is used. The theory is based on the entropy concept from information theory and on the structural pilot model of the human pilot. The method is presented for single axis pilot tracking maneuvers and offers a measure of the human pilot gain employed during its execution. A black-box, state-space, parameter-identified model is used for the plant. Flight test data from a FAR-25 transport aircraft is used to verify the theory of how to determine a measure of the ratio between time spent by the human pilot in the error loop versus in the error rate loop to control the aircraft. This measure is proposed as a test point validation method for PIO flight testing.
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Ye, Cun-En, and 葉存恩. "Flight Simulation and Flying Qualities Evaluation System for Jet Transport Aircraft." Thesis, 2008. http://ndltd.ncl.edu.tw/handle/67873517386496288992.
Full textAbstract:
碩士中華技術學院
飛機系統工程研究所
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The purpose of this research is to develop a desktop flight simulating system. Through this system, the effects of weather hazards on aircraft stability and controllability can be examined. The system includes thrust models, aerodynamic models, and a flight dynamic module. This system has the capability to assist accident investigation and provide the mitigation concepts of weather hazards. The present study uses the data extracted from QAR (Quick Access Recorder) and flight manuals as the inputs of the system and to set up the thrust and aerodynamic models through fuzzy-logic modeling (FLM). The predicted aero databanks for the specific transports are created by the thrust and aerodynamic models to more accurately simulate the real world environment, especially in hazardous weathers, or in loss-of-control situations. The aircraft flies in the atmosphere, it is very difficult to avoid the influence of adverse weather conditions. The effect of adverse atmospheric conditions usually relates to the dynamic aerodynamic effects that result from instantaneous changes of aircraft flight attitude. The pilots are quite easy to improperly operate the aircraft under adverse weather conditions. Among the different turbulence phenomena, the clear-air turbulence is the most important in flight safety since it is hard to detect and predict. An example of comparative analysis for two twin-jet transports encountered clear-air turbulence will be presented in this paper through this system to exhibit the capability in effective evaluations of the performance degradation and variations in stability and controllability of aircraft encountering hazardous weather. The concept of “effective mass” and “effective damping” of the plunging motion is also employed in this paper to analysis aerodynamic environment variations and dynamic effects. This quantitative analysis can be used to evaluate the effects of clear-air turbulence hazards on aircraft stability and controllability.